Air-cooled oil cooler for turbofan engine
AssigneePratt & Whitney Canada Corp.
InventorDANIEL T. ALECU
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Abstract
A turbofan gas turbine engine comprises a nacelle cowl and a core engine. A bypass duct is between an outer surface of a casing of the core engine, and an inner surface of the nacelle cowl. An air channel is in the nacelle cowl, an inlet and an outlet of the air channel being in an outer surface of the nacelle cowl. An oil cooler has at least one oil passage for oil circulation, the air cooler having a first heat exchange surface in the air channel exposed to air circulating in the air channel, the air channel having a second heat exchange surface in the bypass duct exposed to air circulating in the bypass duct. A method for cooling oil in a turbofan gas turbine engine is also provided.
Claims15
A turbofan gas turbine engine comprising:
- a nacelle cowl;
- a core engine;
- a bypass duct between an outer surface of a casing of he core engine, and an inner surface of the nacelle cowl;
- an air channel in the nacelle cowl, an inlet and an outlet of the air channel being in an outer surface of the nacelle cowl;
- and
- an oil cooler having at least one oil passage for oil circulation, the air cooler having a first heat exchange surface in the air channel exposed to air circulating in the air channel, the air channel having a second heat exchange surface in the bypass duct exposed to air circulating in the bypass duct.
A method for cooling oil in a turbofan gas turbine engine, comprising:
- circulating oil in an oil cooler in a nacelle cowl;
- directing air from an inlet in an outer surface of the nacelle cowl into an air channel and on a first heat exchange surface of the oil cooler;
- and
- directing air of a bypass duct on a second heat exchange surface of e oil cooler.
Dependencies are inferred from the claim text.